US4422648A - Ceramic faced outer air seal for gas turbine engines - Google Patents
Ceramic faced outer air seal for gas turbine engines Download PDFInfo
- Publication number
- US4422648A US4422648A US06/389,304 US38930482A US4422648A US 4422648 A US4422648 A US 4422648A US 38930482 A US38930482 A US 38930482A US 4422648 A US4422648 A US 4422648A
- Authority
- US
- United States
- Prior art keywords
- seal
- outer air
- ceramic
- air seal
- edge region
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S277/00—Seal for a joint or juncture
- Y10S277/935—Seal made of a particular material
- Y10S277/943—Ceramic or glass
Definitions
- This invention relates to outer air seals of gas turbine engines, and particularly to seals coated with abradable ceramic materials.
- Outer air seals of some engines are formed of a metallic substrate to which a thermal barrier coating is applied for protection of the seal from the high temperature, working medium gases.
- Ceramic materials are generally known to be effective thermal insulators and are in wide use in such seal application. As long as the ceramic coating remains intact, the ceramic prevents unacceptable deterioration of the metallic form to which it is adhered.
- Durable structures capable of long term, reliable service in the hostile turbine environment are sought. Specific needs are high temperature capability, and good resistance to thermal shock. Additionally, for turbine seal applications the structure must have adequate surface abradability to prevent destructive interference upon the occurrence of rubbing contact of the seal by circumscribed rotor blades and good erosion resistance, particularly at the leading edge of the seal to prevent excessive wear at the incidence of particles entrained in the working medium upon the seal. In some engines the hot working medium gases alone may be erosive.
- ceramic facing material of a turbine outer air seal is formed to first surface density or density near the surface at the leading edge of seal and to a lesser surface density downstream thereof such that the area of the first density is more resistant to wear by foreign particle erosion and the area of lesser density is more easily abraded by passing rotor blades in the installed environment.
- the ceramic facing material is formed of two or more layers of decreasing density with the top, and least dense, layer having a glazed surface at the leading edge region thereof.
- a primary feature of the present invention is the high surface density of the ceramic at the leading edge region of the outer air seal.
- high surface density is achieved by glazing an otherwise porous ceramic.
- Other features of specific embodiments are the porous ceramic in the midregion of the seal and the dense ceramic layer between the porous ceramic and any metallic materials.
- a principal advantage of the present invention is reduced susceptibility of the seal to erosion at the leading edge. Particles entrapped in the working medium stream are deflectable from the glazed surface at the leading edge region without serious erosion. Notwithstanding, good abradability over the rotor blade tips is maintained by leaving surface porosity in that region unaffected.
- FIG. 1 is a simplified side elevation view of a gas turbine engine with a portion of the turbine casing broken away to reveal the relationship of the outer air seal to the turbine blades;
- FIG. 2 is a partial perspective view of the outer air seal of FIG. 1 illustrating the area of high surface density at the leading edge region of the seal;
- FIG. 3 is a partial perspective view of the outer air seal of FIG. 1 illustrating areas of high surface density at both the leading and trailing edge regions of the seal;
- FIG. 4 is one alternate embodiment of the FIG. 2 structure
- FIG. 5 is one alternate embodiment of the FIG. 3 structure.
- FIG. 6 is a photomicrograph of a ceramic coating which has been surface densified to a depth of approximately five thousandths (0.005) of an inch.
- FIG. 1 a preferred turbine outer air seal embodiment for a gas turbine engine. Such an engine is illustrated in FIG. 1.
- the engine principally is formed of a compression section 10, a combustion section 12, and a turbine section 14.
- a rotor assembly 16 extends axially through the engine.
- Rotor blades, such as the single blade 18 illustrated are arranged in rows and extend outwardly on the rotor assembly across a flowpath 20 for working medium gases.
- Each rotor blade has a tip 22.
- a stator assembly 24 having a case 26 houses the rotor assembly 16.
- An outer air seal 28 circumscribes the tips 22 of the rotor blades.
- Each outer air seal is conventionally formed of a plurality of arcuate segments, disposed in end to end relationship about the interior of the engine.
- FIG. 2 A portion of an outer air seal segment 30 fabricated in accordance with the concepts of the present invention is illustrated in FIG. 2.
- Working medium gases of the engine flowpath 20 traverse the seal from the upstream end or leading edge 32 to the downstream end or trailing edge 34.
- the surface of the seal is divided into a leading edge region 36, a midregion 38, and a trailing edge region 40.
- the midregion essentially comprises that portion of the seal surface which is brushed by the passing rotor blades.
- the leading edge region is forward of that portion and the trailing edge region is rearward of that portion.
- each outer air seal segment 30 is formed about a metal substrate 42.
- Multiple layers of graded metal/ceramic material are adhered to the substrate to produce a ceramic faced seal.
- the multiple layers include a bond coat 44 of nickel-chrome-aluminum alloy, two interlayers 46 of mixed zirconium oxide (ZrO 2 ) and cobalt-chromium-aluminum-yttrium (CoCrAlY) alloy, a dense all ceramic layer 48 of zirconium oxide (ZrO 2 ) and a porous all ceramic layer 50 of zirconium oxide (ZrO 2 ).
- the layer materials and application techniques are more fully discussed in U.S. patent application Ser. No. 330,401 which is of common assignee herewith.
- the purpose of the ceramic layers in an outer air seal structure is twofold: to provide a thermal barrier, shielding the substrate from the hot working medium gases of the turbine to which the substrate would be otherwise exposed, and to provide an abradable seal accommodating thermal excursions of the circumscribed rotor blades without destruction interference. Desired material characteristics include good abradability when struck by passing rotor blades and good resistance to erosion. The two characteristics are not always consistent in identically formulated compositions. Achieving both characteristics in the same structure is the object of the present invention.
- Working medium gases of the engine flowpath may contain particles of dirt or other foreign matter and, by the time the medium gases reach the turbine area, may also contain carbon particles from the engine combustor. Such particles as strike the surface of the outer air seal are likely to erode material therefrom, particularly if the material is porous and of moderate or low strength. In some engines the hot gases in and of themselves may be erosive.
- seals of the present invention are fabricated to include an area 52 of high surface density (density near the surface) ceramic in the leading edge region 36 relative to the surface density of the ceramic in the midregion 38 over the rotor blades. Resistance to erosion is improved without destroying desired abradability over the blade tips.
- the area of high surface density is produced by directed energy techniques with localized heating for example by plasma torch or laser. Ceramic at the surface is melted by the directed energy and when cooled forms to a very dense condition and glazed appearance. Particles and gases striking the glazed area deflect from the surface with little erosion.
- the preferred depth of the glazing or high density material is on the order of five to ten thousands of an inch (0.005-0.010 in.) into the ceramic with especially dense structure at the surface. Greater or lesser depths may be acceptable but the depth must first be sufficient to provide erosion resistance over sufficient part life and second not be so great as to be thermally incompatible with the porous substrate to which it is adhered. Thermal incompatibility is likely to cause lateral cracking at the interface between the glazing and the substrate and resultant spalling of the glazed material. When held to depths within the preferred range a desired vertical crack network in the substrate will likely penetrate the glazed surface and spalling will be avoided. In some embodiments it may also be desirable to similarly produce an area 54 of dense or glazed ceramic at the trailing edge region 40 as shown in FIG. 3.
- Dense ceramic such as comprises the first ceramic layer 48, is deposited in the leading edge region 36. Porous ceramic in the layer 50 remains over the blade tips. Dense ceramic may also be deposited at the trailing edge region as shown in FIG. 5.
- ZrO 2 zirconium oxide
- the photomicrograph of FIG. 6 shows the depth of penetration achieved. Densification effects are greatest to a depth of one thousandth (0.001) of an inch with penetration to a depth of approximately five thousandths (0.005) of an inch.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
______________________________________ Gun Distance to Workpiece 11/4" Current 680 amperes Potential 75 volts Arc Gas PrimaryGas Nitrogen Pressure 50 psi Flow Rate 80 CFH SecondaryGas Hydrogen Pressure 50psi Flow Rate 50 CFH Heat Traverse Speed 60 ft/min. Number of Passes 1 Increment between Passes 1/8 inch Substrate Preheat Temperature - start Room temp. Temperature - finish Room temp. Cooling None ______________________________________
Claims (4)
Priority Applications (14)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US06/389,304 US4422648A (en) | 1982-06-17 | 1982-06-17 | Ceramic faced outer air seal for gas turbine engines |
CA000429013A CA1213833A (en) | 1982-06-17 | 1983-05-26 | Ceramic faced outer air seal for gas turbine engines |
FR8309346A FR2528908B1 (en) | 1982-06-17 | 1983-06-06 | AIRTIGHT EXTERIOR BANDAGE COATED WITH CERAMIC MATERIAL FOR GAS TURBINE ENGINES |
BE0/210969A BE897012A (en) | 1982-06-17 | 1983-06-09 | AIRTIGHT EXTERIOR BANDAGE COATED WITH CERAMIC MATERIAL FOR GAS TURBINE ENGINES |
IT21591/83A IT1163508B (en) | 1982-06-17 | 1983-06-13 | EXTERNAL AIR SEAL SEAL COVERED IN CERAMIC FOR GAS TURBINE ENGINES |
GB08316166A GB2121884B (en) | 1982-06-17 | 1983-06-14 | Ceramic faced outer air seal for gas turbine engines |
SE8303368A SE451269B (en) | 1982-06-17 | 1983-06-14 | FOR GAS TURBINE ENGINES DESIGNED WITH CERAMIC SURFACE PROVIDED SEAL TO OUTDOOR AIR |
DE3321477A DE3321477A1 (en) | 1982-06-17 | 1983-06-14 | CERAMIC-COVERED OUTER AIR SEAL FOR GAS TURBINE ENGINES |
NLAANVRAGE8302143,A NL189316C (en) | 1982-06-17 | 1983-06-15 | CERAMICALLY COATED AERIAL GASKET OF A GAS TURBINE ENGINE. |
IL68994A IL68994A0 (en) | 1982-06-17 | 1983-06-15 | Ceramic faced outer air seal for gas turbine engines |
ES523263A ES8404731A1 (en) | 1982-06-17 | 1983-06-15 | Ceramic faced outer air seal for gas turbine engines |
MX197709A MX156511A (en) | 1982-06-17 | 1983-06-17 | IMPROVEMENTS TO EXTERNAL AIR SEAL FOR GAS TURBINE ENGINES |
JP58109109A JPS595808A (en) | 1982-06-17 | 1983-06-17 | External air seal ceramic-faced of gas turbine engine |
SG321/85A SG32185G (en) | 1982-06-17 | 1985-04-30 | Ceramic faced outer air seal for gas turbine engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US06/389,304 US4422648A (en) | 1982-06-17 | 1982-06-17 | Ceramic faced outer air seal for gas turbine engines |
Publications (1)
Publication Number | Publication Date |
---|---|
US4422648A true US4422648A (en) | 1983-12-27 |
Family
ID=23537701
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US06/389,304 Expired - Fee Related US4422648A (en) | 1982-06-17 | 1982-06-17 | Ceramic faced outer air seal for gas turbine engines |
Country Status (14)
Country | Link |
---|---|
US (1) | US4422648A (en) |
JP (1) | JPS595808A (en) |
BE (1) | BE897012A (en) |
CA (1) | CA1213833A (en) |
DE (1) | DE3321477A1 (en) |
ES (1) | ES8404731A1 (en) |
FR (1) | FR2528908B1 (en) |
GB (1) | GB2121884B (en) |
IL (1) | IL68994A0 (en) |
IT (1) | IT1163508B (en) |
MX (1) | MX156511A (en) |
NL (1) | NL189316C (en) |
SE (1) | SE451269B (en) |
SG (1) | SG32185G (en) |
Cited By (48)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4551064A (en) * | 1982-03-05 | 1985-11-05 | Rolls-Royce Limited | Turbine shroud and turbine shroud assembly |
US4566700A (en) * | 1982-08-09 | 1986-01-28 | United Technologies Corporation | Abrasive/abradable gas path seal system |
US4650395A (en) * | 1984-12-21 | 1987-03-17 | United Technologies Corporation | Coolable seal segment for a rotary machine |
US4713300A (en) * | 1985-12-13 | 1987-12-15 | Minnesota Mining And Manufacturing Company | Graded refractory cermet article |
US4732534A (en) * | 1985-10-02 | 1988-03-22 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Rotor blade jacket for axial gas turbines |
US5024884A (en) * | 1984-12-24 | 1991-06-18 | United Technologies Corporation | Abradable seal having particulate erosion resistance |
US5080557A (en) * | 1991-01-14 | 1992-01-14 | General Motors Corporation | Turbine blade shroud assembly |
KR20000006199A (en) * | 1998-06-18 | 2000-01-25 | 레비스 스테픈 이 | Article having durable ceramic coating with localized abradable portion |
US6435824B1 (en) * | 2000-11-08 | 2002-08-20 | General Electric Co. | Gas turbine stationary shroud made of a ceramic foam material, and its preparation |
US6652227B2 (en) * | 2001-04-28 | 2003-11-25 | Alstom (Switzerland) Ltd. | Gas turbine seal |
EP1375696A2 (en) * | 2002-06-10 | 2004-01-02 | MTU Aero Engines GmbH | Coatingsystem for the rotor/stator sealing of a turbo machine |
US6758653B2 (en) | 2002-09-09 | 2004-07-06 | Siemens Westinghouse Power Corporation | Ceramic matrix composite component for a gas turbine engine |
GB2397307A (en) * | 2003-01-20 | 2004-07-21 | Rolls Royce Plc | Abradable Coatings |
US6933061B2 (en) | 2002-12-12 | 2005-08-23 | General Electric Company | Thermal barrier coating protected by thermally glazed layer and method for preparing same |
US20050276688A1 (en) * | 2003-07-25 | 2005-12-15 | Dan Roth-Fagaraseanu | Shroud segment for a turbomachine |
WO2006000174A1 (en) * | 2004-06-29 | 2006-01-05 | Mtu Aero Engines Gmbh | Running-in coating |
US20060171813A1 (en) * | 2005-02-01 | 2006-08-03 | Honeywell International, Inc. | Turbine blade tip and shroud clearance control coating system |
US20070237629A1 (en) * | 2006-04-05 | 2007-10-11 | General Electric Company | Gas turbine compressor casing flowpath rings |
US20080166225A1 (en) * | 2005-02-01 | 2008-07-10 | Honeywell International, Inc. | Turbine blade tip and shroud clearance control coating system |
US20090053045A1 (en) * | 2007-08-22 | 2009-02-26 | General Electric Company | Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud |
US20090053554A1 (en) * | 2007-07-11 | 2009-02-26 | Strock Christopher W | Thermal barrier coating system for thermal mechanical fatigue resistance |
US20090285671A1 (en) * | 2006-08-17 | 2009-11-19 | Siemens Power Generation, Inc. | Vortex cooled turbine blade outer air seal for a turbine engine |
US20100226760A1 (en) * | 2009-03-05 | 2010-09-09 | Mccaffrey Michael G | Turbine engine sealing arrangement |
US20100247291A1 (en) * | 2009-03-30 | 2010-09-30 | Tholen Susan M | Gas turbine engine article having columnar microstructure |
CN102094165A (en) * | 2010-12-27 | 2011-06-15 | 北京工业大学 | Highly wear-resistant mechanical seal moving ring and manufacturing method thereof |
US20110154801A1 (en) * | 2009-12-31 | 2011-06-30 | Mahan Vance A | Gas turbine engine containment device |
US8100640B2 (en) | 2007-10-25 | 2012-01-24 | United Technologies Corporation | Blade outer air seal with improved thermomechanical fatigue life |
DE102010048147A1 (en) * | 2010-10-11 | 2012-04-12 | Mtu Aero Engines Gmbh | Layer system for rotor / stator seal of a turbomachine and method for producing such a layer system |
US20130017058A1 (en) * | 2011-07-15 | 2013-01-17 | Joe Christopher R | Blade outer air seal having partial coating |
US20130170963A1 (en) * | 2012-01-04 | 2013-07-04 | United Technologies Corporation | Hybrid blade outer air seal for gas turbine engine |
US8528339B2 (en) | 2007-04-05 | 2013-09-10 | Siemens Energy, Inc. | Stacked laminate gas turbine component |
EP2412932A3 (en) * | 2010-07-27 | 2015-02-25 | United Technologies Corporation | Blade outer air seal and repair method |
WO2015050706A1 (en) * | 2013-10-02 | 2015-04-09 | United Technologies Corporation | Segmented ceramic coating interlayer |
EP3018296A1 (en) * | 2014-11-07 | 2016-05-11 | Rolls-Royce Corporation | Gas turbine engine assembly with an abradable blade track and corresponding formation method |
JP2016524081A (en) * | 2013-06-28 | 2016-08-12 | シーメンス アクティエンゲゼルシャフト | Gas turbine and heat shield for gas turbine |
US20160251976A1 (en) * | 2013-10-02 | 2016-09-01 | United Technologies Corporation | Turbine abradable air seal system |
US9551353B2 (en) | 2013-08-09 | 2017-01-24 | General Electric Company | Compressor blade mounting arrangement |
US9737933B2 (en) | 2012-09-28 | 2017-08-22 | General Electric Company | Process of fabricating a shield and process of preparing a component |
US20170276007A1 (en) * | 2016-03-23 | 2017-09-28 | United Technologies Corporation | Outer Airseal Insulated Rub Strip |
US9995165B2 (en) | 2011-07-15 | 2018-06-12 | United Technologies Corporation | Blade outer air seal having partial coating |
US20180231014A1 (en) * | 2017-02-13 | 2018-08-16 | United Technologies Corporation | Multilayer abradable coating |
US20180355742A1 (en) * | 2017-06-13 | 2018-12-13 | Safran Aircraft Engines | Turbine engine and air-blowing sealing method |
US20190032504A1 (en) * | 2017-07-27 | 2019-01-31 | Rolls-Royce Corporation | Multilayer abradable coatings for high-performance systems |
US20190085865A1 (en) * | 2017-09-19 | 2019-03-21 | United Technologies Corporation | Turbine engine seal for high erosion environment |
US20190360351A1 (en) * | 2018-05-22 | 2019-11-28 | Rolls-Royce Corporation | Tapered abradable coatings |
US10900371B2 (en) | 2017-07-27 | 2021-01-26 | Rolls-Royce North American Technologies, Inc. | Abradable coatings for high-performance systems |
US20210180467A1 (en) * | 2019-12-13 | 2021-06-17 | Pratt & Whitney Canada Corp. | Dual density abradable panels |
US11566531B2 (en) | 2020-10-07 | 2023-01-31 | Rolls-Royce Corporation | CMAS-resistant abradable coatings |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0729201Y2 (en) * | 1988-11-08 | 1995-07-05 | 京セラ株式会社 | Turbine blade tip sealing device |
GB9325135D0 (en) * | 1993-12-08 | 1994-02-09 | Rolls Royce Plc | Manufacture of wear resistant components |
US5439348A (en) * | 1994-03-30 | 1995-08-08 | United Technologies Corporation | Turbine shroud segment including a coating layer having varying thickness |
GB9726710D0 (en) * | 1997-12-19 | 1998-02-18 | Rolls Royce Plc | Turbine shroud ring |
DE19950417A1 (en) * | 1999-10-20 | 2001-04-26 | Abb Patent Gmbh | Component for gas turbine, with base body and protective covering made of ceramic material |
GB0911500D0 (en) | 2009-07-03 | 2009-08-12 | Rolls Royce Plc | Rotor blade over-tip leakage control |
EP2317079B1 (en) | 2009-10-30 | 2020-05-20 | Ansaldo Energia Switzerland AG | Abradable coating system |
US8727712B2 (en) | 2010-09-14 | 2014-05-20 | United Technologies Corporation | Abradable coating with safety fuse |
US9175575B2 (en) * | 2012-01-04 | 2015-11-03 | General Electric Company | Modification of turbine engine seal abradability |
US20160305319A1 (en) * | 2015-04-17 | 2016-10-20 | General Electric Company | Variable coating porosity to influence shroud and rotor durability |
US10494945B2 (en) * | 2016-04-25 | 2019-12-03 | United Technologies Corporation | Outer airseal abradable rub strip |
US10294962B2 (en) * | 2017-06-30 | 2019-05-21 | United Technologies Corporation | Turbine engine seal for high erosion environment |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3001806A (en) * | 1954-10-14 | 1961-09-26 | Macks Elmer Fred | Seal |
US3126149A (en) * | 1964-03-24 | Foamed aluminum honeycomb motor | ||
US3339933A (en) * | 1965-02-24 | 1967-09-05 | Gen Electric | Rotary seal |
US3778184A (en) * | 1972-06-22 | 1973-12-11 | United Aircraft Corp | Vane damping |
US4257735A (en) * | 1978-12-15 | 1981-03-24 | General Electric Company | Gas turbine engine seal and method for making same |
US4295786A (en) * | 1978-08-04 | 1981-10-20 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Composite seal for turbomachinery |
US4336276A (en) * | 1980-03-30 | 1982-06-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Fully plasma-sprayed compliant backed ceramic turbine seal |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3836156A (en) * | 1971-07-19 | 1974-09-17 | United Aircraft Canada | Ablative seal |
GB2053367B (en) * | 1979-07-12 | 1983-01-26 | Rolls Royce | Cooled shroud for a gas turbine engine |
US4280975A (en) * | 1979-10-12 | 1981-07-28 | General Electric Company | Method for constructing a turbine shroud |
IT1163729B (en) * | 1979-10-15 | 1987-04-08 | Pozzi L Mecc | ROTARY DRUM HEAT EXCHANGER |
GB2081817B (en) * | 1980-08-08 | 1984-02-15 | Rolls Royce | Turbine blade shrouding |
US4492765A (en) * | 1980-08-15 | 1985-01-08 | Gte Products Corporation | Si3 N4 ceramic articles having lower density outer layer, and method |
-
1982
- 1982-06-17 US US06/389,304 patent/US4422648A/en not_active Expired - Fee Related
-
1983
- 1983-05-26 CA CA000429013A patent/CA1213833A/en not_active Expired
- 1983-06-06 FR FR8309346A patent/FR2528908B1/en not_active Expired
- 1983-06-09 BE BE0/210969A patent/BE897012A/en not_active IP Right Cessation
- 1983-06-13 IT IT21591/83A patent/IT1163508B/en active
- 1983-06-14 DE DE3321477A patent/DE3321477A1/en active Granted
- 1983-06-14 SE SE8303368A patent/SE451269B/en not_active IP Right Cessation
- 1983-06-14 GB GB08316166A patent/GB2121884B/en not_active Expired
- 1983-06-15 IL IL68994A patent/IL68994A0/en not_active IP Right Cessation
- 1983-06-15 NL NLAANVRAGE8302143,A patent/NL189316C/en not_active IP Right Cessation
- 1983-06-15 ES ES523263A patent/ES8404731A1/en not_active Expired
- 1983-06-17 MX MX197709A patent/MX156511A/en unknown
- 1983-06-17 JP JP58109109A patent/JPS595808A/en active Granted
-
1985
- 1985-04-30 SG SG321/85A patent/SG32185G/en unknown
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3126149A (en) * | 1964-03-24 | Foamed aluminum honeycomb motor | ||
US3001806A (en) * | 1954-10-14 | 1961-09-26 | Macks Elmer Fred | Seal |
US3339933A (en) * | 1965-02-24 | 1967-09-05 | Gen Electric | Rotary seal |
US3778184A (en) * | 1972-06-22 | 1973-12-11 | United Aircraft Corp | Vane damping |
US4295786A (en) * | 1978-08-04 | 1981-10-20 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Composite seal for turbomachinery |
US4257735A (en) * | 1978-12-15 | 1981-03-24 | General Electric Company | Gas turbine engine seal and method for making same |
US4336276A (en) * | 1980-03-30 | 1982-06-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Fully plasma-sprayed compliant backed ceramic turbine seal |
Cited By (82)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4551064A (en) * | 1982-03-05 | 1985-11-05 | Rolls-Royce Limited | Turbine shroud and turbine shroud assembly |
US4566700A (en) * | 1982-08-09 | 1986-01-28 | United Technologies Corporation | Abrasive/abradable gas path seal system |
US4650395A (en) * | 1984-12-21 | 1987-03-17 | United Technologies Corporation | Coolable seal segment for a rotary machine |
US5024884A (en) * | 1984-12-24 | 1991-06-18 | United Technologies Corporation | Abradable seal having particulate erosion resistance |
US4732534A (en) * | 1985-10-02 | 1988-03-22 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Rotor blade jacket for axial gas turbines |
US4713300A (en) * | 1985-12-13 | 1987-12-15 | Minnesota Mining And Manufacturing Company | Graded refractory cermet article |
US5080557A (en) * | 1991-01-14 | 1992-01-14 | General Motors Corporation | Turbine blade shroud assembly |
EP0965730A3 (en) * | 1998-06-18 | 2001-02-14 | United Technologies Corporation | Article having durable ceramic coating with localised abradable portion |
US6358002B1 (en) * | 1998-06-18 | 2002-03-19 | United Technologies Corporation | Article having durable ceramic coating with localized abradable portion |
KR20000006199A (en) * | 1998-06-18 | 2000-01-25 | 레비스 스테픈 이 | Article having durable ceramic coating with localized abradable portion |
US6435824B1 (en) * | 2000-11-08 | 2002-08-20 | General Electric Co. | Gas turbine stationary shroud made of a ceramic foam material, and its preparation |
US6652227B2 (en) * | 2001-04-28 | 2003-11-25 | Alstom (Switzerland) Ltd. | Gas turbine seal |
US7178808B2 (en) | 2002-06-10 | 2007-02-20 | Mtu Aero Engines Gmbh | Layer system for the rotor/stator seal of a turbomachine |
EP1375696A2 (en) * | 2002-06-10 | 2004-01-02 | MTU Aero Engines GmbH | Coatingsystem for the rotor/stator sealing of a turbo machine |
EP1375696A3 (en) * | 2002-06-10 | 2005-04-27 | MTU Aero Engines GmbH | Coatingsystem for the rotor/stator sealing of a turbo machine |
US6758653B2 (en) | 2002-09-09 | 2004-07-06 | Siemens Westinghouse Power Corporation | Ceramic matrix composite component for a gas turbine engine |
US6933061B2 (en) | 2002-12-12 | 2005-08-23 | General Electric Company | Thermal barrier coating protected by thermally glazed layer and method for preparing same |
GB2397307A (en) * | 2003-01-20 | 2004-07-21 | Rolls Royce Plc | Abradable Coatings |
US20050276688A1 (en) * | 2003-07-25 | 2005-12-15 | Dan Roth-Fagaraseanu | Shroud segment for a turbomachine |
US7479328B2 (en) * | 2003-07-25 | 2009-01-20 | Rolls-Royce Deutschland Ltd & Co Kg | Shroud segment for a turbomachine |
WO2006000174A1 (en) * | 2004-06-29 | 2006-01-05 | Mtu Aero Engines Gmbh | Running-in coating |
DE102004031255B4 (en) * | 2004-06-29 | 2014-02-13 | MTU Aero Engines AG | inlet lining |
US8895134B2 (en) | 2004-06-29 | 2014-11-25 | Mtu Aero Engines Gmbh | Apparatus and method for coating a compressor housing |
US20090214824A1 (en) * | 2004-06-29 | 2009-08-27 | Mtu Aero Engines Gmbh | Apparatus and method for coating a compressor housing |
US20060171813A1 (en) * | 2005-02-01 | 2006-08-03 | Honeywell International, Inc. | Turbine blade tip and shroud clearance control coating system |
US20080166225A1 (en) * | 2005-02-01 | 2008-07-10 | Honeywell International, Inc. | Turbine blade tip and shroud clearance control coating system |
US7473072B2 (en) * | 2005-02-01 | 2009-01-06 | Honeywell International Inc. | Turbine blade tip and shroud clearance control coating system |
US7510370B2 (en) * | 2005-02-01 | 2009-03-31 | Honeywell International Inc. | Turbine blade tip and shroud clearance control coating system |
US20070237629A1 (en) * | 2006-04-05 | 2007-10-11 | General Electric Company | Gas turbine compressor casing flowpath rings |
US20090285671A1 (en) * | 2006-08-17 | 2009-11-19 | Siemens Power Generation, Inc. | Vortex cooled turbine blade outer air seal for a turbine engine |
US7665955B2 (en) | 2006-08-17 | 2010-02-23 | Siemens Energy, Inc. | Vortex cooled turbine blade outer air seal for a turbine engine |
US8528339B2 (en) | 2007-04-05 | 2013-09-10 | Siemens Energy, Inc. | Stacked laminate gas turbine component |
US20090053554A1 (en) * | 2007-07-11 | 2009-02-26 | Strock Christopher W | Thermal barrier coating system for thermal mechanical fatigue resistance |
US20090053045A1 (en) * | 2007-08-22 | 2009-02-26 | General Electric Company | Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud |
US8100640B2 (en) | 2007-10-25 | 2012-01-24 | United Technologies Corporation | Blade outer air seal with improved thermomechanical fatigue life |
US8534995B2 (en) | 2009-03-05 | 2013-09-17 | United Technologies Corporation | Turbine engine sealing arrangement |
US20100226760A1 (en) * | 2009-03-05 | 2010-09-09 | Mccaffrey Michael G | Turbine engine sealing arrangement |
US20100247291A1 (en) * | 2009-03-30 | 2010-09-30 | Tholen Susan M | Gas turbine engine article having columnar microstructure |
US8105014B2 (en) | 2009-03-30 | 2012-01-31 | United Technologies Corporation | Gas turbine engine article having columnar microstructure |
US9062565B2 (en) | 2009-12-31 | 2015-06-23 | Rolls-Royce Corporation | Gas turbine engine containment device |
US20110154801A1 (en) * | 2009-12-31 | 2011-06-30 | Mahan Vance A | Gas turbine engine containment device |
EP2412932A3 (en) * | 2010-07-27 | 2015-02-25 | United Technologies Corporation | Blade outer air seal and repair method |
DE102010048147B4 (en) * | 2010-10-11 | 2016-04-21 | MTU Aero Engines AG | Layer system for rotor / stator seal of a turbomachine and method for producing such a layer system |
DE102010048147A1 (en) * | 2010-10-11 | 2012-04-12 | Mtu Aero Engines Gmbh | Layer system for rotor / stator seal of a turbomachine and method for producing such a layer system |
EP2439379A3 (en) * | 2010-10-11 | 2017-07-12 | MTU Aero Engines AG | Coating system for rotor/stator seal of a fluid flow engine and method for producing such a coating system |
US8992169B2 (en) | 2010-10-11 | 2015-03-31 | Mtu Aero Engines Gmbh | Layer system for rotor/stator seal of a turbomachine and method for producing this type of layer system |
CN102094165A (en) * | 2010-12-27 | 2011-06-15 | 北京工业大学 | Highly wear-resistant mechanical seal moving ring and manufacturing method thereof |
US9062558B2 (en) * | 2011-07-15 | 2015-06-23 | United Technologies Corporation | Blade outer air seal having partial coating |
US20130017058A1 (en) * | 2011-07-15 | 2013-01-17 | Joe Christopher R | Blade outer air seal having partial coating |
EP2546463A3 (en) * | 2011-07-15 | 2014-08-13 | United Technologies Corporation | Blade outer air seal having partial coating |
US9995165B2 (en) | 2011-07-15 | 2018-06-12 | United Technologies Corporation | Blade outer air seal having partial coating |
US9169739B2 (en) * | 2012-01-04 | 2015-10-27 | United Technologies Corporation | Hybrid blade outer air seal for gas turbine engine |
US10392958B2 (en) | 2012-01-04 | 2019-08-27 | United Technologies Corporation | Hybrid blade outer air seal for gas turbine engine |
US20130170963A1 (en) * | 2012-01-04 | 2013-07-04 | United Technologies Corporation | Hybrid blade outer air seal for gas turbine engine |
US9737933B2 (en) | 2012-09-28 | 2017-08-22 | General Electric Company | Process of fabricating a shield and process of preparing a component |
US10828701B2 (en) | 2012-09-28 | 2020-11-10 | General Electric Company | Near-net shape shield and fabrication processes |
JP2016524081A (en) * | 2013-06-28 | 2016-08-12 | シーメンス アクティエンゲゼルシャフト | Gas turbine and heat shield for gas turbine |
US9551353B2 (en) | 2013-08-09 | 2017-01-24 | General Electric Company | Compressor blade mounting arrangement |
WO2015050706A1 (en) * | 2013-10-02 | 2015-04-09 | United Technologies Corporation | Segmented ceramic coating interlayer |
US9938849B2 (en) * | 2013-10-02 | 2018-04-10 | United Technologies Corporation | Turbine abradable air seal system |
US20160251976A1 (en) * | 2013-10-02 | 2016-09-01 | United Technologies Corporation | Turbine abradable air seal system |
US10760443B2 (en) | 2013-10-02 | 2020-09-01 | Raytheon Technologies Corporation | Turbine abradable air seal system |
EP3018296A1 (en) * | 2014-11-07 | 2016-05-11 | Rolls-Royce Corporation | Gas turbine engine assembly with an abradable blade track and corresponding formation method |
US10132185B2 (en) * | 2014-11-07 | 2018-11-20 | Rolls-Royce Corporation | Additive process for an abradable blade track used in a gas turbine engine |
US20160130969A1 (en) * | 2014-11-07 | 2016-05-12 | Rolls-Royce Corporation | Additive process for an abradable blade track used in a gas turbine engine |
US10247027B2 (en) * | 2016-03-23 | 2019-04-02 | United Technologies Corporation | Outer airseal insulated rub strip |
US20170276007A1 (en) * | 2016-03-23 | 2017-09-28 | United Technologies Corporation | Outer Airseal Insulated Rub Strip |
US20180231014A1 (en) * | 2017-02-13 | 2018-08-16 | United Technologies Corporation | Multilayer abradable coating |
US11209010B2 (en) * | 2017-02-13 | 2021-12-28 | Raytheon Technologies Corporation | Multilayer abradable coating |
US20180355742A1 (en) * | 2017-06-13 | 2018-12-13 | Safran Aircraft Engines | Turbine engine and air-blowing sealing method |
US11208909B2 (en) * | 2017-06-13 | 2021-12-28 | Safran Aircraft Engines | Turbine engine and air-blowing sealing method |
US10900371B2 (en) | 2017-07-27 | 2021-01-26 | Rolls-Royce North American Technologies, Inc. | Abradable coatings for high-performance systems |
US10858950B2 (en) * | 2017-07-27 | 2020-12-08 | Rolls-Royce North America Technologies, Inc. | Multilayer abradable coatings for high-performance systems |
US20190032504A1 (en) * | 2017-07-27 | 2019-01-31 | Rolls-Royce Corporation | Multilayer abradable coatings for high-performance systems |
US11506073B2 (en) * | 2017-07-27 | 2022-11-22 | Rolls-Royce North American Technologies, Inc. | Multilayer abradable coatings for high-performance systems |
US11149744B2 (en) * | 2017-09-19 | 2021-10-19 | Raytheon Technologies Corporation | Turbine engine seal for high erosion environment |
US20190085865A1 (en) * | 2017-09-19 | 2019-03-21 | United Technologies Corporation | Turbine engine seal for high erosion environment |
US10808565B2 (en) * | 2018-05-22 | 2020-10-20 | Rolls-Royce Plc | Tapered abradable coatings |
US20190360351A1 (en) * | 2018-05-22 | 2019-11-28 | Rolls-Royce Corporation | Tapered abradable coatings |
US20210180467A1 (en) * | 2019-12-13 | 2021-06-17 | Pratt & Whitney Canada Corp. | Dual density abradable panels |
US11215070B2 (en) * | 2019-12-13 | 2022-01-04 | Pratt & Whitney Canada Corp. | Dual density abradable panels |
US11566531B2 (en) | 2020-10-07 | 2023-01-31 | Rolls-Royce Corporation | CMAS-resistant abradable coatings |
Also Published As
Publication number | Publication date |
---|---|
FR2528908B1 (en) | 1985-11-29 |
NL189316B (en) | 1992-10-01 |
GB8316166D0 (en) | 1983-07-20 |
ES523263A0 (en) | 1984-05-16 |
SE451269B (en) | 1987-09-21 |
FR2528908A1 (en) | 1983-12-23 |
SE8303368L (en) | 1983-12-18 |
CA1213833A (en) | 1986-11-12 |
BE897012A (en) | 1983-10-03 |
IL68994A0 (en) | 1983-10-31 |
ES8404731A1 (en) | 1984-05-16 |
JPH0133644B2 (en) | 1989-07-14 |
IT1163508B (en) | 1987-04-08 |
DE3321477A1 (en) | 1983-12-29 |
IT8321591A0 (en) | 1983-06-13 |
GB2121884A (en) | 1984-01-04 |
SG32185G (en) | 1985-11-15 |
JPS595808A (en) | 1984-01-12 |
GB2121884B (en) | 1985-02-13 |
NL189316C (en) | 1993-03-01 |
SE8303368D0 (en) | 1983-06-14 |
MX156511A (en) | 1988-09-05 |
NL8302143A (en) | 1984-01-16 |
DE3321477C2 (en) | 1992-09-03 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4422648A (en) | Ceramic faced outer air seal for gas turbine engines | |
US4594053A (en) | Housing for a fluid flow or jet engine | |
US4289446A (en) | Ceramic faced outer air seal for gas turbine engines | |
US6358002B1 (en) | Article having durable ceramic coating with localized abradable portion | |
US4764089A (en) | Abradable strain-tolerant ceramic coated turbine shroud | |
US4936745A (en) | Thin abradable ceramic air seal | |
US6224963B1 (en) | Laser segmented thick thermal barrier coatings for turbine shrouds | |
US4914794A (en) | Method of making an abradable strain-tolerant ceramic coated turbine shroud | |
US4377371A (en) | Laser surface fusion of plasma sprayed ceramic turbine seals | |
US4503130A (en) | Prestressed ceramic coatings | |
US11732595B2 (en) | Abrasive tip blade manufacture methods | |
US4273824A (en) | Ceramic faced structures and methods for manufacture thereof | |
US4481237A (en) | Method of applying ceramic coatings on a metallic substrate | |
EP2971533B1 (en) | Turbine blade tip treatment for industrial gas turbines | |
US4430360A (en) | Method of fabricating an abradable gas path seal | |
JP2006036632A (en) | 7FA+e STAGE 1 ABRADABLE COATING AND METHOD FOR MAKING THE SAME | |
GB2317899A (en) | Abradable seal assembly | |
JPH0715141B2 (en) | Heat resistant parts | |
JP2000144365A (en) | Thermal barrier coating member, production of thermal barrier coating member and high temperature gas turbine using thermal barrier coating member | |
Mohammad et al. | Criteria for abradable coatings to enhance the performance of gas turbine engines | |
GB2117269A (en) | Thermal barrier coating | |
EP3725909A1 (en) | Geometrically segmented thermal barrier coating with spall interrupter features | |
EP3907375A1 (en) | Thermal barrier coating with reduced edge crack initiation stress and high insulating factor | |
Nava et al. | Ceramic Abradable Coatings for Applications up to 1100° C | |
Bill et al. | Method of fabricating an abradable gas path seal |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: UNITED TECHNOLOGIES CORPORATION, HARTFORD, CT A CO Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNORS:EATON, HARRY E.;NOVAK, RICHARD C.;REEL/FRAME:004009/0246 Effective date: 19820610 |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, PL 96-517 (ORIGINAL EVENT CODE: M170); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 4 |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, PL 96-517 (ORIGINAL EVENT CODE: M171); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 8 |
|
FEPP | Fee payment procedure |
Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
LAPS | Lapse for failure to pay maintenance fees | ||
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 19951227 |
|
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |